IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0758903
(2010-04-13)
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등록번호 |
US-8290641
(2012-10-16)
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발명자
/ 주소 |
- Marstall, Jerry Lee
- Mozaffar, Shakeel
|
출원인 / 주소 |
- Pilot Disorientation Prevention Technologies, L.L.C.
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대리인 / 주소 |
Thomas, Kayden, Horstemeyer & Risley, LLP.
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인용정보 |
피인용 횟수 :
2 인용 특허 :
6 |
초록
▼
Aircraft attitude systems are provided. A representative aircraft attitude system includes: a detection system operative to determine an attitude of an aircraft in which the detection system is mounted; a warning system operative to alert a pilot when the attitude of the aircraft corresponds to at l
Aircraft attitude systems are provided. A representative aircraft attitude system includes: a detection system operative to determine an attitude of an aircraft in which the detection system is mounted; a warning system operative to alert a pilot when the attitude of the aircraft corresponds to at least one predefined attitude parameter from a set of predefined attitude parameters, the predefined attitude parameters including pitch, bank and yaw; and a recovery system operative to provide progressive flight control positioning directives to the pilot for returning the aircraft to a flight attitude within the predefined attitude parameters.
대표청구항
▼
1. An aircraft attitude system for use by a pilot for warning of an aircraft departure from a desired aircraft attitude and directives for the pilot to manually return an aircraft to a desired aircraft attitude, the aircraft attitude system comprising: a detection system having a first accelerometer
1. An aircraft attitude system for use by a pilot for warning of an aircraft departure from a desired aircraft attitude and directives for the pilot to manually return an aircraft to a desired aircraft attitude, the aircraft attitude system comprising: a detection system having a first accelerometer such that the first accelerometer determines a first attitude parameter of an aircraft in which the detection system is mounted;a user interface for receiving manual inputs corresponding to a set of pilot-selectable attitude parameters of the aircraft, the pilot-selectable attitude parameters including maximum pitch angle and maximum bank angle; andan instrument display having a recovery system, the recovery system receiving information corresponding to the first attitude parameter such that, responsive to the first attitude parameter of the aircraft corresponding to the first pilot-selectable attitude parameter, the recovery system provides progressive flight control positioning directives to the pilot via the instrument display for manually returning the aircraft to a flight attitude within the pilot-selectable attitude parameters;the instrument display displaying the progressive flight control positioning directives as arrows illuminated on the display, with a length of a first of the arrows corresponding to a magnitude of the first attitude parameter detected by the accelerometer such that a shorter length indicates a smaller angle of the first attitude parameter and a longer arrow indicates a larger angle of the first attitude parameter;wherein:the first of the arrows is displayed with an overall length corresponding to the magnitude of the first attitude parameter; andresponsive to the attitude excursion exceeding the first pilot-selectable attitude parameter, the first of the arrows has a first segment and a second segment, the first segment extending from a base of the first of the arrows and being of a first length corresponding to the magnitude of the first pilot-selectable attitude parameter, the second segment extending from the first segment such that the pilot is presented with a visual depiction corresponding to an extent of the attitude excursion. 2. The system of claim 1, wherein the arrows are selectively displayable at 90 degree increments about the instrument display, with the arrows pointing radially outwardly from the center of the instrument display. 3. The system of claim 1, wherein a color of the arrow displayed by the instrument display indicates magnitude of an attitude excursion exceeding the first pilot-selectable attitude parameter. 4. The system of claim 1, wherein the user interface receives manual inputs corresponding to pilot-selectable attitude parameters for each of multiple phases of flight such that each of the multiple phases is associated with an independent set of the pilot-selectable attitude parameters. 5. The system of claim 4, wherein: a first of the multiple phases of flight corresponds to a take-off phase; andthe pilot-selectable attitude parameters associated with the take-off phase additionally include a minimum pitch angle. 6. The system of claim 1, wherein a rate of change in length of the first of the arrows corresponds to a rate of change of the first attitude parameter of the aircraft such that the pilot is provided with a visual indication of rate of recovery from an attitude excursion. 7. The system of claim 1, wherein the first segment exhibits a first color and the second segment exhibits a second color. 8. The system of claim 7, wherein the first color is green and the second color is red. 9. The system of claim 1, wherein, responsive to the first attitude parameter indicating a right bank, the instrument display displays the first of the arrows as a left arrow. 10. The system of claim 1, wherein, responsive to the first attitude parameter indicating a left bank, the instrument display displays the first of the arrows as a right arrow. 11. The system of claim 1, wherein, responsive to the first attitude parameter indicating a nose-down pitch, the instrument display displays the first of the arrows as an up arrow. 12. The system of claim 1, wherein, responsive to the first attitude parameter indicating a nose-up pitch, the instrument display displays the first of the arrows as a down arrow. 13. The system of claim 1, further comprising a warning system having a speaker and electrically communicating with the detection system, the warning system receiving information corresponding to the first attitude parameter such that, responsive to the first attitude parameter of the aircraft corresponding to a first of the pilot-selectable attitude parameters, the warning system provides an audible warning via the speaker. 14. The system of claim 13, wherein the warning system provides a verbal warning directive via the speaker. 15. The system of claim 13, wherein the warning system alerts the pilot regarding flight attitude correspondence to at least one of the pilot-selectable attitude parameters responsive to expiration of a timing delay, the timing delay being actuated by initial correspondence of the flight attitude to the at least one of the pilot-selectable attitude parameters. 16. The system of claim 15, wherein the warning system overrides the timing delay based on a rate of change of at least one of the pilot-selectable attitude parameters corresponding to a predefined excessive rate of change such that the pilot is alerted without regard to the timing delay. 17. The system of claim 15, wherein the warning system alerts the pilot with both verbal and visual warning directives. 18. The system of claim 17, wherein the instrument display displays the visual warning directives, which comprise words corresponding to flight control inputs for the pilot to manually return the aircraft to within the pilot-selectable attitude parameters. 19. The system of claim 1, further comprising: a processor; anda memory having instructions stored therein, the instructions being executable by the processor to provide the progressive flight control positioning directives to the pilot via the instrument display for manually returning the aircraft to a flight attitude within the pilot-selectable attitude parameters.
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